Axial retention assembly for combustor components of a gas turbine engine

Abstract

The present subject matter is directed to an axial retention assembly for combustor components of a gas turbine engine. The axial retention assembly may include a combustor having include a liner defining a liner aperture extending therethrough. Additionally, the combustor may further include a sleeve defining a sleeve aperture extending therethrough, with the sleeve positioned radially outward from and at least partially circumferentially positioned around the liner. Furthermore, the axial retention assembly may include a frame having a mounting projection positioned within the sleeve aperture. Moreover, the axial retention assembly may include a clamp plate adjustably coupled to the frame. In addition, the axial retention assembly may include a clamp plate adjustment rod extending through the liner aperture and threadingly engaging the clamp plate such that relative movement between the liner and the sleeve along the axial centerline is reduced.

What is claimed is: 
     
       1. An axial retention assembly for combustor components of a gas turbine engine, the axial retention assembly comprising:
 a combustor defining an axial centerline extending between a forward end of the combustor and an aft end of the combustor, the combustor further defining a radial direction extending orthogonally outward from the axial centerline, the combustor including a liner defining an aperture extending therethrough, the combustor further including a sleeve defining a sleeve aperture extending therethrough, the sleeve positioned radially outward from and at least partially circumferentially positioned around the liner; 
 a frame including a mounting projection positioned within the sleeve aperture; 
 a clamp plate adjustably coupled to the frame; 
 a clamp plate adjustment rod extending through the liner aperture and threadingly engaging the clamp plate such that relative movement between the liner and the sleeve along the axial centerline is reduced. 
 
     
     
       2. The axial retention assembly of  claim 1 , wherein the clamp plate is positioned between the liner and the sleeve in the radial direction. 
     
     
       3. The axial retention assembly of  claim 1 , wherein rotation of the clamp plate adjustment rod relative to the liner moves the clamp plate between the liner and the frame in the radial direction. 
     
     
       4. The axial retention assembly of  claim 1 , wherein the mounting projection extends outward from the frame along in the radial direction. 
     
     
       5. The axial retention assembly of  claim 1 , wherein the frame comprises a first wall and a second wall, the mounting projection extending outward from the first wall, the clamp plate being adjustably coupled to the second wall. 
     
     
       6. The axial retention assembly of  claim 5 , wherein the first wall is oriented perpendicular to the second wall. 
     
     
       7. The axial retention assembly of  claim 5 , wherein the first wall is positioned between the liner and the sleeve in the radial direction. 
     
     
       8. The axial retention assembly of  claim 5 , wherein the second wall extends inward along the radial direction from the first wall. 
     
     
       9. The axial retention assembly of  claim 1 , further comprising:
 a clamp plate coupling rod coupled to the clamp plate, wherein the frame defines an elongated slot extending therethrough, the clamp plate coupling rod extending through the elongated slot. 
 
     
     
       10. The axial retention assembly of  claim 9 , further comprising:
 a first fastener threadingly engaging the clamp plate coupling rod; 
 a second fastener threadingly engaging the clamp plate coupling rod, the first fastener being positioned between the second fastener and the frame along the axial centerline, 
 wherein the second fastener prevents the first fastener from threadingly disengaging the clamp plate coupling rod. 
 
     
     
       11. A gas turbine engine, comprising:
 a combustor defining an axial centerline extending between a forward end of the combustor and an aft end of the combustor, the combustor further defining a radial direction extending orthogonally outward from the axial centerline, the combustor comprising:
 a liner defining an aperture extending therethrough and a combustion chamber therein; 
 a sleeve defining a sleeve aperture extending therethrough, the sleeve positioned radially outward from and at least partially circumferentially positioned around the liner, the sleeve and the liner defining a flow passage therebetween; and 
 
 a plurality of axial retention tools, each axial retention tool comprising:
 a frame including a mounting projection positioned within the sleeve aperture; 
 a clamp plate adjustably coupled to the frame; 
 a clamp plate adjustment rod extending through the liner aperture and threadingly engaging the clamp plate such that relative movement between the liner and the sleeve along the axial centerline is reduced. 
 
 
     
     
       12. The gas turbine engine of  claim 11 , wherein each of the plurality of axial retention tools are circumferentially spaced apart from each other around the combustor. 
     
     
       13. The gas turbine engine of  claim 11 , wherein the clamp plate is positioned between the liner and the sleeve in the radial direction. 
     
     
       14. The gas turbine engine of  claim 11 , wherein rotation of the clamp plate adjustment rod relative to the liner moves the clamp plate between the liner and the frame in the radial direction. 
     
     
       15. The gas turbine engine of  claim 11 , wherein the mounting projection extends outward from the frame along in the radial direction. 
     
     
       16. The gas turbine engine of  claim 11 , wherein each frame comprises a first wall and a second wall, the mounting projection extending outward from the first wall, the clamp plate being adjustably coupled to the second wall. 
     
     
       17. The gas turbine engine of  claim 16 , wherein the first wall is oriented perpendicular to the second wall. 
     
     
       18. The gas turbine engine of  claim 16 , wherein the first wall is positioned between the liner and the sleeve in the radial direction. 
     
     
       19. The gas turbine engine of  claim 11 , wherein each axial retention tool further comprises:
 a clamp plate coupling rod coupled to the clamp plate, wherein the frame defines an elongated slot extending therethrough, the clamp plate coupling rod extending through the elongated slot. 
 
     
     
       20. The gas turbine engine of  claim 19 , wherein each axial retention tool further comprises:
 a first fastener threadingly engaging the clamp plate coupling rod; 
 a second fastener threadingly engaging the clamp plate coupling rod, the first fastener being positioned between the second fastener and the frame along the axial centerline, 
 wherein the second fastener prevents the first fastener from threadingly disengaging the clamp plate coupling rod.